Aerojet solid rocket engine. 13 kN. Improved Orion motor was a bi-phase propellant system with thrust levels of 84.5 kN during the first four seconds of motor burn, trailing off to 13.3 kN at burnout at 25 seconds.

The Improved Orion motor was a bi-phase propellant system that results in thrust levels of approximately 84.5 kN during the first four seconds of motor burn then trailing off to approximately 13.3 kN until burnout around 25 seconds. The fins were generally configured to provide a burn out spin rate of four cycles per second.

Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

Associated Stages

Improved Orion-1 Solid propellant rocket stage. Loaded mass 400 kg. Thrust 13.00 kN. The Improved Orion motor was a bi-phase propellant system that results in thrust levels of approximately 84.5 kN during the first four seconds of motor burn then trailing off to approximately 13.3 kN until burnout around 25 seconds. The fins were generally configured to provide a burn out spin rate of four cycles per second. More...